Gas turbine motor of reduced



1 1 6, 1 fwd. 2 mm 3 w+ S GDP PM M S m N, m I LD mm AG 5 R mmm 1. EF. BB w Mw mm REF h B C mm 2 U T 5% Hf 4 me M T. w 4 2 e n H J Patented June24, 1952 GAS TURBINE-MOTOR or REDUCED DIMENSIONS Roger Jean Imbert andMarcel Henri Louis St:-

dille, Paris, France, assignors to Societe Rateau Societe Anonyme),Paris, France, a company of France, and Rene Anxionnaz, Paris, FranceApplication August 27, 1945, Serial No. 612,866 In France January 8,1942 Section 1, Public Law 690, August 8 1946 Patent expires January 8,1962 3 Claims. 1

For certain problems it is of interest to have available motors havingdimensions as small as possible particularly in diameter.

Gas turbine motors are particularly satisfactory from this point ofview. Nevertheless the arrangement of the combustion chamber may causean inconvenient increase in dimensions and the object of the presentinvention is to reduce this increase.

According to the invention the combustion chamber is subdivided intoseveral chambers connected in parallel between the compressor and theturbine and distributed around the axis of the motor or of thecompressor.

The following description with reference to the accompanying drawing,given by way of nonlimiting example, will explain how the invention maybe carried into effect, the features apparent both from the drawing andthe description forming, as will be understood, a part thereof.

Fig. 1 is a schematic view in section of a gas turbine motor of a knowntype.

Fig. 2 is an axial section of a motor in conf ormity with the invention.

Fig. 3 is a transverse section on line III-III of Fig. 2.

Figs. 4 and 5 are transverse sections of two modifications.

A gas turbine motor is constituted essentially, as shown in Fig. 1, byan air compressor C, by one or more combustion chambers Ch and by anexpansion turbine T which is for example divided into two elements, oneof which, Tc, controls the compressor, and the other of which, Tm,provides the motive power properly socalled.

The arrangement of the combustion chambers forming the subject of thepresent invention permits of housing the whole of the motor in a volumehaving a diameter as small as possible, whilst at the same timemaintaining conditions which are necessary for the good operation ofthese chambers and comprising in particular:

1. A length of chamber sufficient for obtaining a combustion which is ascomplete as possible.

2. A double circulation, cold air outside-hot gas inside, in such a wayas to recuperate a maximum quantity of calories lost externally byconvection and radiation. This arrangement permits likewise of notputtin to Work the internal hot wall, the pressure being supported bythe cold external wall.

3. A satisfactory accessibility of the burners.

According to Figs. 2 and 3, the motor comprises a certain number ofcombustion chambers Ch disposed around the compressor. These combustionchambers have cylindricalwalls in such a way as to obtain maximumlightness of the casing for a given pressure. They have double walls I,2, the cold air coming from the compressor circulating externally of thechambers between the envelopes I and 2, the hot gases internally. Theburners or atomisers b disposed in the heads are particularly accessibleand easy to inspect and to dismantle. Finally the length dimension beingfree within the limit of that of the compressor, a length necessary forthe development of the flame and for complete combustion may easily beprovided. The external diameter of the turbine Ta necessary for drivingthe compressor being greater than the diameter of the compressor, theconnection of such chambers at the inlet of the turbines is particularlyfavourable, and the external diameter may be equal to or only slightlygreater than that of the turbines. From the point of view of expansionit is of interest that the chambers are connected to the compressor onlyby connecting tubes 3 supplying air under pressure, the chambers thenbeing able to expand freely.

In order to obtain a minimum diameter it is of advantage to increase thenumber of chambers to such a point that they substantially touch oneanother laterally. In doing this, however, the total weight isincreased, as also the number of burners or atomisers, and theirdimensions are decreased, which may increase difficulties in supplyingthe combustible.

When a small dimension in one direction is more important than in theother, the chambers may be arranged only on a portion of a circle. whichsurrounds the compressor, or better on two oppositely disposed sectors,as illustrated in Fig. 5.

Fig. 4 relates to another particular construction of the inventioncomprising combustion chambers which have a lenticular cross-section insuch a way as to obtain a very small volume with a moderate number ofchambers. By reason of the increase in the radius of curvature of thewalls it would be necessary to make them of greater thickness than inthe case of Fig. 3, and therefore to increase the weight. According tothe present invention this disadvantage may be remedied by providing aconnection between the different chambers by small bars 4. Thearrangement can still expand freely diametrically and lengthwise.

What we claim is:

1. A gas turbine power plant comprising in combination an axial-flowmulti-stage air compressor having a discharge passage, an axial-flow gasturbine coaxial with said compressor, adjacent thereto and adapted todrive same, said turbine having a gas-intake passage, the overalldiameter of said turbine being greater than the over-all diameter ofsaid compressor, and a plurality of separate, elongated combustionchambers of lenticular cross-section, each having an air inlet connectedto said discharge passage and a gas outlet connected to' said gas-intakepassage, said elongated chambers being located around said compressor,in the vicinity thereof, and extending in a direction substantiallyparallel to the axis of the compressor. 1

2. A gas turbine power plant comprising in combination an axial-flowmulti-stage air compressor having a discharge passage, an axial-flow gasturbine coaxial with said compressor, adjacent thereto and. adapted todrive same, said turbine having a gas-intake passage, the over-alldiameter of said turbine being greater than the over-all diameter ofsaid compressor, and a plurality of separate, elongated combustionchambers, each including a tubular outer casing of lenticularcross-section connected at one end to said discharge passage and atubular inner cas ing of lenticular cross-section inside said outercasing and spaced therefrom, connected at one end to said gas-intakepassage, said ends being in the vicinity of one another, the combustionchamber being supported from said ends, the other ends of said outercasing and said inner casing being respectively closed and open, saidelongated chambers being located around said compressor, in the vicinitythereof, and extending in a direction substantially parallel to the axisof the compressor.

3. A gas turbine power plant comprising in combination an air compressorhaving a discharge passage, a gas turbine coaxial with said compressorand adjacent thereto, said turbine having a gas-intake passage, and apluralit of separate, elongated combustion chambers of lenticularcross-section, each having an air inlet connected to said dischargepassage and a gas outlet connected to said gas-intake passage, saidelongated chambers extending substantially parallel to the axis of thecompressor.

ROGER JEAN INEBERT. MARCEL HENRI LOUIS SEDILLE.

REFERENCES CITED The following references are of record in the file ofthis patent:

UNITED STATES PATENTS Number Name Date 1,346,509 Olhovsky July 13, 19202,085,761 Lysholm July 6, 1937 2,256,198 Hahn Sept. 16, 194 2,326,072Seippel 'Aug. 3, 1943 2,332,866 Miiller Oct. 26, 1943 2,396,068 YoungashMar. 5, 1946 2,398,654 Lubbock et a1 Apr. 16, 1946 2,399,046 LarrecqApr. 23, 1946 2,404,334 Whittle July 16, 1946 FOREIGN PATENTS NumberCountry Date Great Britain Apr. 16, 1931

